Aeroplane stabilizing mechanism



A. K. LONGREN.

AEROPLANE STABILIZING MECHANISIVI.

APPLICATION FILED IAN.3I. 1918.

Patented Nov. 1l, 1919.

ya I 5 i Fig. III is a plan view of the same.

a on;

ALBIN K. IOlll'G-Rlllq', 0F KANSAS CITY, ,MISSOURI 'I AERoPLANn STABILIZING MEcHANIsM-i.

Application iled January 31,

ToaZZ-whom tfmay concern:

f Be it known that I, ALBIN'K. LONGREN, a citizen of the United States, residing at Kansas City, in the county of Jackson and State of Missouri, have invented certain new and useful Improvements in Aeroplane Stabilizing Mechanism; and I do declare the following to be al i full, clear, and exact description ofthe invention, such as will enable others skilled in the art to'which it appertains toY make and use` the same, reference being had to the accompanying drawings, and to the letters and figures of reference marked thereon, whichv form a part of this specification.

This invention relates to aeroplane 'stabilzing mechanism, and more particularly to automatically operable aerodynamic means for maintaining an aeroplane in lateral or transverse balance underj varying conditions. a y

One of the objects of the invention is to provide astabilizing mechanism which may be conveniently attached to a known type of aeroplane without materially altering the yconstruction of the aeroplane, the advantage being that the existing aeroplanes may be conveniently equipped with the 'invention in an expeditions manner.

Another object of the invention is to provide av stabilizer including a hanging weighted actuator in coperative relation with certain` control members and the ailerons of the,aeroplane so that when the aeroplane is tilted rout of the horizontal, the hanging weighted actuator which will have a normal tendency to maintain the perpeni dicular, will have suflicient force to cause thev ailerons to tilt the plane at the precise angle necessary to prevent any possible side slip.

In the drawings, y

Figure I is a side elevation of a portion of an aeroplane showing stabilizing mechanism constructed 'according to the present invention, applied thereto.

Fig. II'is an enlarged side view of the, stabilizing` mechanism.

Fig. IVis a front elevation of the pendulum control device.

Referring more in detail to the drawings:

1 designates an aeroplane of a type whereonthe present stabilizing mechanism may be Specication of Letters Patent.

rammed New. 11, 191e. 191s. vserial No. 214,627.

utilized, comprising a fuselage 2, propeller '3, upper and lower planes 4 and 5 respec- Supported by the pivot 11, in such a manner that it may pivot in a horizontal plane, is a laterally swinging member shown as a shaft12, the opposite ends of which terminate at a slight distance ahead andback of lixed to the'lrearward end of the said member 12 is a yoke member i13 comprising vertically alining arms '14-14 which support -a vertical pivot pin 15"; the opposite ends of the pin being extended beyond the yoke arms and pivotally supporting a stream line airbalanced aerofoil or fin 16, the latter being maintained in a vertical plane and rovided at its forward edge with a recess 1 whereinto the supporting yoke is extended, and which has oppositely opening sockets 18-18 arranged in vertical alinement in its .upper and lower edges, wherein the ends of the pin 15 are pivotally seated to support the aerofoil. t f

Pivotally supported from the forward end of the member 12 by a bolt or cap screw 20 threaded into the end of the .shaft is a hanging actuator 21 having a suitable weight 22 adjustably fixed at its lower end whereby vertical alinement of the actuator is maintained and having a short lever portion 23 extending upwardly from pivotal point, provided at its upper e nd with an eye 24' wherein the ends of oppositely extending cables 25-25 are iixed, the latter leading vfrom the actuator respectively o ver sheave wheels 26-26 mounted on opposite sides of the shaft 13 and horizontally in alinement with the upper end of the lever armf 23,' at the upper ends of arms 27-27 extending from a collar 28; that is Ifixed. on the shaft 12 the edgesy of the supporting plane 4, and e adjacent its forward end. From the sheave t wheels the cables are extended rearwardly andare attached respectivelytobracket arms 30-30 fixed perpendicularly to the opposite sides of the aerofoil at points in vertical alinement with the pivot pin 15, so that swinging movement of the weighted end of the hanging actuator toward either end of the plane will cause the aerofoil to pivot about its support and its rear end to move toward the low'er end of the plane.

Also fixed to the shaft 12, at a slight distance ahead of the bearing 11, and extending in opposite directions are cables 32-32 which extend about sheave wheels 33-33, fixed adjacent the opposite outer ends of the plane 4, and are attached at their ends to brackets 34-34, extending upwardly from the hingedly mounted ailerons 35-35 at the rear corners of the upper plane. With this connection it is apparent that movement of the forward end of the shaft 12 in one direction will raise the aileron at one end of the plane, and lower the one at the opposite end and vice versa to automatically move the plane to stable position. v

With the stabilizing mechanism so constructed and mounted, and the cables 25-25 and 32-32 attached respectively to the swinging member 12 and ailerons as described, in operation, while the plane maintains a lateral balance, the aerofoil simply follows in alinement with the vdirection of travel, but should one end of the plane drop, due to changeable air currents, loss of control, or for other reasons, the weight 22, to maintain its vertical position, will swing toward the lower end of the plane. This movement of the weight, by its connection through the cables 25-25 moves the rearward end of the aerofoil or fin toward the lower end of the plane and presents that side of the aerofoil to the wind pressure, which moves the aerofoil and that part of the shaft supporting the same toward the higher end of the plane until the aerofoil is brought into alinement with the direction of travel. This movement of the shaft 12 through the cables 32-32 raises the free' edge of the aileron 35 and lowers the free edge of the opposite aileron so that the higher end of the plane is moved downwardly vand theo lower end upwardly to bring the plane back to its lateral balance, whereupon the weight moves to neutral position and the aerofoil again assumes a position in alinement with its supporting shaft.

It is to be understood that cables 32- and 32 are fast to the ailerons 35 and 35 beneath the plane 4 and pass over pulleys 38 and 38 to assist cables 32 and 32 in causing synchronous movement of the ailerons as will be clearly understood.

Automatic banking at turns is valso obtained through operation of the weight, it

being apparent that when a turn is made the' weight will swing toward the outside of the turn, this actuates the aerofoil to move the forward end of the shaft 12 toward the outside of the turn, causing the ailerons to tilt so as to raise the plane at the outer side and correspondingly lower it on the inner side. It is also apparent that the weight on the actuator may be so adjusted that centrifugal force thereon at the turn will swing it sufficiently to actuate the ailerons through the shaft 12 to give the plane the precise incline necessary, considering the degree of the curve or turn being made and the rate of travel of the machine, to prevent any possible side slip in either direction.

With the parts so constructed, it is apparent that the plane cannot be thrown from its lateral balance, and it is banked properly without attention from the aviator.

It is to be understood that the aerofoil 16 does not take the place of the ordinary, rudder and is not intended as a steering device. The ordinary steering-is accomplished in the usual manner under the control of the aviator, the aerofoil 16 serving the purpose of actuating the ailerons 35--35 under the control of the weighted actuator.

Having thus described my invention, what I claim as new therein and desire to secure by Letters-Patent is 1. In combination with an aeroplane having stabilizing ailerons thereon for maintaining the same in transverse balance, a stabilizing device comprising a horizontally disposed, pivotally mounted supporting shaft, a vertical aerofoil pivotally mounted at one end of said shaft, a weighted actuator' mounted at the opposite end of said shaft and having a portion extending above its pivotal point, sheave wheels supported from the supporting shaft at opposite sides of the actuator, and cables fixed to said weighted actuator extension, extending over said sheave wheels and operatively attached to the actuator which moves the supporting shaft, and cables operatively connecting the supporting shaft with the ailerons to actuate the latter under the control of the weighted actuator.

2. In combination with an aeroplane having stabilizing ailerons at its opposite ends for maintaining the same in transverse balance, a stabilizing device comprising a horizontally disposed supporting shaft pivotallyw supported adjacent its forward end, a vertical aerofoil.pivotallymountd at the rearward end of said shaft having laterally extending brackets on its opposite sides whereby it may be moved on its support, a weighted actuator mounted at the forward' end of the shaft having a portion extending' above its pivotal point, a bracket fixed to the' forward end of the shaft, sheave Wheels supported by said bracket at opposite sides of the actuator extension, and cables fixed to to said extension, extending in opposite drectons and over said sheave Wheels and at- 5 tached to said aerofol brackets so that Inovenlent 0f the actuator actuates the aerofol and also rotates the supporting shaft n the direction of the actuator movement, and cables operatively connecting the supporting shaft with the ailerons to actuatethe latter l0 under the control of the actuator.

In testimony whereof I aix my signature.

ALBIN K. LONGREN. 

